CN104565189A - Multilayer constraining and damping implementation method for vibration damping of case of aeroengine - Google Patents
Multilayer constraining and damping implementation method for vibration damping of case of aeroengine Download PDFInfo
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- CN104565189A CN104565189A CN201410805756.3A CN201410805756A CN104565189A CN 104565189 A CN104565189 A CN 104565189A CN 201410805756 A CN201410805756 A CN 201410805756A CN 104565189 A CN104565189 A CN 104565189A
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- constraining
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
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- General Engineering & Computer Science (AREA)
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to a multilayer constraining and damping implementation method for vibration damping of a case of an aeroengine. The method comprises the following steps: (1) taking lightweight aluminum foil as a constraining material, sequentially sticking a viscoelastic material and the constraining material, carrying out multilayer constraining and damping processing on the case of the aeroengine, and establishing a multilayer constraining and damping case vibration analysis model; (2) determining the number of layers of a multilayer constraining and damping structure by adopting an improved transfer matrix method; (3) enabling the surface to be stuck of the case to keep a certain temperature; (4) gradually sticking a constraining and damping material to the case starting from one end of the constraining and damping material; (5) verifying the vibration damping effectiveness of the multilayer constraining and damping processed case. The method has the advantages that the method is simple and is easy to implement, and the vibration stress of the case can be effectively lowered, so that the fatigue damage resistance of the case is improved; multiple layers of constraining and damping have very good bonding performance and are firm in sticking, so that the case has a good vibration damping suppression effect.
Description
Technical field
The present invention relates to aeroengine field, particularly a kind of multilayer damping-constraining implementation methods for aero-engine casing vibration damping.
Background technique
Aero-engine casing vibration stress is excessive, can cause the fatigue damage of casing, thus affects aeroengine security of operation.Lay free damping or damping-constraining can play good effectiveness in vibration suppression, particularly damping-constraining and have good inhibitory action on casing surface to broad-band random vibration response, and do not change base structure, method is simple, safe and reliable.Paste viscoelastic layer and restraint layer successively at body structure surface, namely form traditional constrained damping structure.In order to increase damping vibration attenuation effect, viscoelastic layer, restraint layer, viscoelastic layer, restraint layer etc. can be pasted successively at body structure surface, forming multilayer damping-constraining structure.Research shows: under identical associated mass, and multilayer damping-constraining has better damping vibration attenuation effect than traditional constraints damping, adopts multilayer damping-constraining, effectively can reduce the vibration stress of casing, improves the ability of its antifatigue damage.
Summary of the invention
The object of this invention is to provide a kind of multilayer damping-constraining implementation methods for aero-engine casing vibration damping, adopt the transfer matrix method improved, calculate the vibration characteristics of multilayer damping-constraining casing, analysis constraint material thickness, viscoelastic material thickness and the number of plies, on the impact of multilayer damping-constraining casing modal loss factor, determine multilayer damping-constraining structural parameter and the number of plies.
The invention provides a kind of multilayer damping-constraining implementation methods for aero-engine casing vibration damping, it is characterized in that: the described multilayer damping-constraining implementation methods for aero-engine casing vibration damping, comprises the following steps:
Step one, adopts lightweight aluminium foil as constraint material, on the pending surface of aero-engine casing, pastes viscoelastic material and constraint material successively, carries out multilayer damping-constraining process, set up multilayer damping-constraining casing vibration analysis model to aero-engine casing.
Step 2, adopt the transfer matrix method improved, calculate the vibration characteristics of multilayer damping-constraining casing, analysis constraint material thickness, viscoelastic material thickness and the number of plies, on the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
Step 3, before carrying out multilayer damping-constraining process, first cleans adhesive surface casing, guarantees that adhesive surface is clean without greasy dirt.In order to ensure the soundness of pasting, the surface to be pasted of casing should be made to keep certain temperature.
Step 4, from damping-constraining material one end, successively pastes on casing by damping-constraining material, should guarantee bubble-free between visco-elastic damping material and casing in taping process, should be placed more than 24 hours after having pasted.
Step 5, test casing and the vibration stress through multilayer damping-constraining process rear housing, contrast is pasted before and after multilayer damping-constraining process, the change of the vibration stress of casing, the vibration damping validity of checking multilayer damping-constraining processor box.
The multilayer damping-constraining structure built in described step one is followed successively by casing, viscoelastic layer, restraint layer, viscoelastic layer and restraint layer, and viscoelastic layer and restraint layer have identical thickness respectively.
Adopt the transfer matrix method of improvement in described step 2, calculate restraint layer thickness, viscoelastic layer thickness and the number of plies to the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
In described step 3, adopt isopropanol to clean casing surface to be pasted, during stickup, the surface to be pasted of casing and the temperature of constraint damping material are not less than 20 DEG C, between being preferably 40 ~ 60 DEG C.
Advantage of the present invention:
Multilayer damping-constraining implementation methods for aero-engine casing vibration damping of the present invention, adopt multilayer damping-constraining technology, aero-engine casing is processed, do not change case structure, method is simple, easy to implement, effectively can reduce the vibration stress of casing, thus improve its antifatigue lesion capability.Its implementation methods ensures that multilayer damping-constraining has good adhesive property, firm pasting, makes casing have good vibration damping inhibition.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is multilayer damping-constraining structural representation;
In figure, 1 is casing layer, and 2 is viscoelastic layer, and 3 is restraint layer.
Embodiment
Embodiment 1
Present embodiments provide a kind of multilayer damping-constraining implementation methods for aero-engine casing vibration damping, it is characterized in that: the described multilayer damping-constraining implementation methods for aero-engine casing vibration damping, comprises the following steps:
Step one, adopts lightweight aluminium foil as constraint material, on the pending surface of aero-engine casing, pastes viscoelastic material and constraint material successively, carries out multilayer damping-constraining process, set up multilayer damping-constraining casing vibration analysis model to aero-engine casing.
Step 2, adopt the transfer matrix method improved, calculate the vibration characteristics of multilayer damping-constraining casing, analysis constraint material thickness, viscoelastic material thickness and the number of plies, on the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
Step 3, before carrying out multilayer damping-constraining process, first cleans adhesive surface casing, guarantees that adhesive surface is clean without greasy dirt.In order to ensure the soundness of pasting, the surface to be pasted of casing should be made to keep certain temperature.
Step 4, from damping-constraining material one end, successively pastes on casing by damping-constraining material, should guarantee bubble-free between visco-elastic damping material and casing in taping process, should be placed more than 24 hours after having pasted.
Step 5, test casing and the vibration stress through multilayer damping-constraining process rear housing, contrast is pasted before and after multilayer damping-constraining process, the change of the vibration stress of casing, the vibration damping validity of checking multilayer damping-constraining processor box.
The multilayer damping-constraining structure built in described step one is followed successively by casing, viscoelastic layer, restraint layer, viscoelastic layer and restraint layer, and viscoelastic layer and restraint layer have identical thickness respectively.
Adopt the transfer matrix method of improvement in described step 2, calculate restraint layer thickness, viscoelastic layer thickness and the number of plies to the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
In described step 3, adopt isopropanol to clean casing surface to be pasted, during stickup, the surface to be pasted of casing and the temperature of constraint damping material are 40 DEG C.
Embodiment 2
Present embodiments provide a kind of multilayer damping-constraining implementation methods for aero-engine casing vibration damping, it is characterized in that: the described multilayer damping-constraining implementation methods for aero-engine casing vibration damping, comprises the following steps:
Step one, adopts lightweight aluminium foil as constraint material, on the pending surface of aero-engine casing, pastes viscoelastic material and constraint material successively, carries out multilayer damping-constraining process, set up multilayer damping-constraining casing vibration analysis model to aero-engine casing.
Step 2, adopt the transfer matrix method improved, calculate the vibration characteristics of multilayer damping-constraining casing, analysis constraint material thickness, viscoelastic material thickness and the number of plies, on the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
Step 3, before carrying out multilayer damping-constraining process, first cleans adhesive surface casing, guarantees that adhesive surface is clean without greasy dirt.In order to ensure the soundness of pasting, the surface to be pasted of casing should be made to keep certain temperature.
Step 4, from damping-constraining material one end, successively pastes on casing by damping-constraining material, should guarantee bubble-free between visco-elastic damping material and casing in taping process, should be placed more than 24 hours after having pasted.
Step 5, test casing and the vibration stress through multilayer damping-constraining process rear housing, contrast is pasted before and after multilayer damping-constraining process, the change of the vibration stress of casing, the vibration damping validity of checking multilayer damping-constraining processor box.
The multilayer damping-constraining structure built in described step one is followed successively by casing, viscoelastic layer, restraint layer, viscoelastic layer and restraint layer, and viscoelastic layer and restraint layer have identical thickness respectively.
Adopt the transfer matrix method of improvement in described step 2, calculate restraint layer thickness, viscoelastic layer thickness and the number of plies to the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
In described step 3, adopt isopropanol to clean casing surface to be pasted, during stickup, the surface to be pasted of casing and the temperature of constraint damping material are 60 DEG C.
Embodiment 3
Present embodiments provide a kind of multilayer damping-constraining implementation methods for aero-engine casing vibration damping, it is characterized in that: the described multilayer damping-constraining implementation methods for aero-engine casing vibration damping, comprises the following steps:
1. adopt the transfer matrix method of improvement, the vibration characteristics of comparing calculation casing and multilayer damping-constraining casing, adopt lightweight aluminium foil to be constraint material, determine that restraint layer thickness is 0.13mm, viscoelastic layer thickness is 0.05mm.
2., before multilayer damping-constraining process being carried out to casing, first adopting isopropanol to clean adhesive surface, wipe oil, in order to ensure the soundness of pasting, making casing and damping-constraining material temperature remain on 50 DEG C.
3. multilayer damping-constraining process is carried out to casing, from damping-constraining material one end, successively damping-constraining material is pasted on casing, bubble-free between visco-elastic damping material and casing bonding plane is guaranteed in the process of pasting, and place more than 24 hours, make damping-constraining material and casing paste intact.
4. test casing and the vibration stress through multilayer damping-constraining process rear housing, contrast is pasted before and after multilayer damping-constraining process, the change of the vibration stress of casing, the vibration damping validity of checking multilayer damping-constraining processor box.Test result is shown in Table 1.
Dynamic stress rest result before and after the process of table 1 casing multilayer damping-constraining
As known from Table 1: after carrying out multilayer damping-constraining process to casing, resonant frequency and rotation speed change are very little, but vibration stress have dropped about 50%.
Finally should be noted that, above embodiment is only in order to illustrate technological scheme of the present invention and unrestricted, although with reference to preferred embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that, can modify to technological scheme of the present invention or equivalent replacement, and not departing from aim and the scope of the technical program, it all should be encompassed in the middle of right of the present invention.
Claims (4)
1. for a multilayer damping-constraining implementation methods for aero-engine casing vibration damping, it is characterized in that: the described multilayer damping-constraining implementation methods for aero-engine casing vibration damping, comprises the following steps:
Step one, adopts lightweight aluminium foil as constraint material, on the pending surface of aero-engine casing, pastes viscoelastic material and constraint material successively, carries out multilayer damping-constraining process, set up multilayer damping-constraining casing vibration analysis model to aero-engine casing.
Step 2, adopt the transfer matrix method improved, calculate the vibration characteristics of multilayer damping-constraining casing, analysis constraint material thickness, viscoelastic material thickness and the number of plies, on the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
Step 3, before carrying out multilayer damping-constraining process, first cleans adhesive surface casing, guarantees that adhesive surface is clean without greasy dirt.In order to ensure the soundness of pasting, the surface to be pasted of casing should be made to keep certain temperature.
Step 4, from damping-constraining material one end, successively pastes on casing by damping-constraining material, should guarantee bubble-free between visco-elastic damping material and casing in taping process, should be placed more than 24 hours after having pasted.
Step 5, test casing and the vibration stress through multilayer damping-constraining process rear housing, contrast is pasted before and after multilayer damping-constraining process, the change of the vibration stress of casing, the vibration damping validity of checking multilayer damping-constraining processor box.
2. according to the multilayer damping-constraining implementation methods for aero-engine casing vibration damping according to claim 1, it is characterized in that: the multilayer damping-constraining structure built in described step one is followed successively by casing, viscoelastic layer, restraint layer, viscoelastic layer and restraint layer, and viscoelastic layer and restraint layer have identical thickness respectively.
3. according to the multilayer damping-constraining implementation methods for aero-engine casing vibration damping according to claim 1, it is characterized in that: the transfer matrix method adopting improvement in described step 2, calculate restraint layer thickness, viscoelastic layer thickness and the number of plies to the impact of multilayer damping-constraining casing modal loss factor, determine the number of plies of multilayer damping-constraining structure.
4. according to the multilayer damping-constraining implementation methods for aero-engine casing vibration damping according to claim 1, it is characterized in that: in described step 3, isopropanol is adopted to clean casing surface to be pasted, during stickup, the surface to be pasted of casing and the temperature of constraint damping material are not less than 20 DEG C, between being preferably 40 ~ 60 DEG C.
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| CN201410805756.3A CN104565189A (en) | 2014-12-19 | 2014-12-19 | Multilayer constraining and damping implementation method for vibration damping of case of aeroengine |
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| CN107219048A (en) * | 2017-06-19 | 2017-09-29 | 中国船舶重工集团公司第七0四研究所 | Local restriction damping layer vibration test frock |
| CN108388701A (en) * | 2018-01-30 | 2018-08-10 | 南京理工大学 | A kind of ballistic limit computational methods of gapless double-level-metal casing |
| CN108555612A (en) * | 2018-03-14 | 2018-09-21 | 华中科技大学 | A kind of surface assistance processing method for reducing machining workpiece vibration |
| CN109669253A (en) * | 2019-01-31 | 2019-04-23 | 中国科学院西安光学精密机械研究所 | Large caliber reflecting mirror vibration damping flexible support structure and mirror assembly |
| CN110594355A (en) * | 2019-09-27 | 2019-12-20 | 中国科学院沈阳自动化研究所 | Dynamic vibration absorber array for space science experiment cabinet and manufacturing method thereof |
| CN112580157A (en) * | 2020-11-26 | 2021-03-30 | 南京航空航天大学 | Vibration reduction design method for internal and external casings of aero-engine under extremely low frequency condition |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107219048A (en) * | 2017-06-19 | 2017-09-29 | 中国船舶重工集团公司第七0四研究所 | Local restriction damping layer vibration test frock |
| CN108388701A (en) * | 2018-01-30 | 2018-08-10 | 南京理工大学 | A kind of ballistic limit computational methods of gapless double-level-metal casing |
| CN108388701B (en) * | 2018-01-30 | 2021-09-03 | 南京理工大学 | Ballistic limit calculation method of gapless double-layer metal casing |
| CN108555612A (en) * | 2018-03-14 | 2018-09-21 | 华中科技大学 | A kind of surface assistance processing method for reducing machining workpiece vibration |
| CN109669253A (en) * | 2019-01-31 | 2019-04-23 | 中国科学院西安光学精密机械研究所 | Large caliber reflecting mirror vibration damping flexible support structure and mirror assembly |
| CN110594355A (en) * | 2019-09-27 | 2019-12-20 | 中国科学院沈阳自动化研究所 | Dynamic vibration absorber array for space science experiment cabinet and manufacturing method thereof |
| CN110594355B (en) * | 2019-09-27 | 2023-12-22 | 中国科学院沈阳自动化研究所 | Dynamic vibration absorber array for space science experiment cabinet and manufacturing method thereof |
| CN112580157A (en) * | 2020-11-26 | 2021-03-30 | 南京航空航天大学 | Vibration reduction design method for internal and external casings of aero-engine under extremely low frequency condition |
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